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TECHNICAL PAPERS

Film-Cooled Turbine Endwall in a Transonic Flow Field: Part I—Aerodynamic Measurements

[+] Author and Article Information
Friedrich Kost, Martin Nicklas

Institute of Propulsion Technology, German Aerospace Center (DLR), 37073 Göttingen, Germany

J. Turbomach 123(4), 709-719 (Feb 01, 2001) (11 pages) doi:10.1115/1.1400112 History: Received February 01, 2001
Copyright © 2001 by ASME
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References

Sieverding,  C. H., 1985, “Recent Progress in the Understanding of Basic Aspects of Secondary Flows in Turbine Blade Passages,” ASME J. Eng. Gas Turbines Power, 107, pp. 248–257.
Sieverding,  C. H., and Wilputte,  P., 1981, “Influence of Mach Number and Endwall Cooling on Secondary Flows in a Straight Nozzle Cascade,” ASME J. Eng. Power, 103, pp. 257–264.
Friedrichs,  S., Hodson,  H. P., and Dawes,  W. N., 1997, “Aerodynamic Aspects of Endwall Film-Cooling,” ASME J. Turbomach., 119, pp. 786–793.
Langston,  S., 1980, “Crossflow in a Turbine Cascade Passage,” ASME J. Eng. Power, 102, pp. 866–874.
Blair,  M. F., 1974, “An Experimental Study of Heat Transfer and Film Cooling on Large-Scale Turbine Endwalls,” ASME J. Heat Transfer, 96, pp. 524–529.
Bourguignon, A. E., 1985, “Etudes des Transferts Thermiques sur les Plates-Formes de Distributeur de Turbine avec et sans Film de Refroidissement,” AGARD-CP-390, pp. 12-1–12-9.
Granser, D., and Schulenburg, T., 1990, “Prediction and Measurement of Film Cooling Effectiveness for a First-Stage Turbine Vane Shroud,” ASME Paper No. 90-GT-95.
Burd, S. W., and Simon, T. W., 2000, “Effects of Slot Bleed Injection Over a Contoured Endwall on Nozzle Guide Vane Cooling Performance: Part I—Flow Field Measurements,” ASME Paper No. 2000-GT-199.
Georgiou, D. P., Papavasilopoulos, V. A., and Alevisos, M., 1996, “Experimental Contribution on the Significance and the Control by Transverse Injection of the Horseshoe Vortex,” ASME Paper No. 96-GT-255.
Nicklas, M., 2000, “Filmgekühlte Turbinenplattform in transsonischem Strömungsfeld,” Dissertation, Rheinisch-Westfälische Technische Hochschule Aachen; additionally published as DLR-FB 2000-10, Cologne.
Schodl,  R., 1980, “A Laser-Two-Focus (L2F) Velocimeter for Automatic Flow Vector Measurements in the Rotating Components of Turbomachines,” ASME J. Fluids Eng., 102, pp. 412–419.
Kost, F., and Kapteijn, C., 1997, “Application of Laser-Two-Focus Velocimetry to Transonic Turbine Flows,” Proc. 7th Int. Conf. on Laser Anemometry—Advances and Applications, University of Karlsruhe, Germany.
Kost, F., 1993, “Längswirbelentstehung in einem Turbinenlaufrad mit konischen Seitenwänden,” Dissertation, University of Göttingen; DLR-FB 93-13 (ISSN 0939-2963).
Kapteijn, C., 1995, “Wake Development Downstream of a Transonic Turbine Inlet Guide Vane With Trailing Edge Ejection,” AGARD-CP-571, Paper No. 14.
Friedrichs, S., and Hodson, H. P., 1994, “The Ammonia and Diazo Surface Coating Technique for Measuring Adiabatic Film Cooling Effectiveness,” 12th Symp. on Measuring Techniques for Transonic and Supersonic Flows in Cascades and Turbomachines, Prague, Czech Republic.
Haslinger, W., and Hennecke, D. K., 1996, “The Ammonia and Diazo Technique With CO2-Calibration for Highly Resolving and Accurate Measurement of Adiabatic Film Cooling Effectiveness With Application to a Row of Holes,” ASME Paper No. 96-GT-438.
Kost, F., and Nicklas, M., 2000, “Der aerodynamische Einfluss von Plattformkühlung auf das wandnahe Strömungsfeld des Turbinenstators T6.2,” DLR Internal Report IB 223-2000 A 03, Göttingen.
Amecke, J., and Šafařı́k, P., 1995, “Data Reduction of Wake Flow Measurements With Injection of Another Gas,” Forschungsbericht DLR-FB 95-32, Cologne.
Horlock, J. H., 1966, Axial Flow Turbines, Robert E. Krieger Publishing Company, Malabar, USA.
Lawaczeck, O., 1977, “The Influence of Jets of Cooling Air Exhausted From the Trailing Edges of a Supercritical Turbine Cascade on the Aerodynamic Data,” AGARD-CP-229, Paper No. 30.

Figures

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Sketch of secondary flow features in a turbine passage according to Langston 4
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Geometry of the stator and the cooling configuration
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Section through cooling geometry (schematic)
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Schlieren picture of flow field in the stator at Ma2is=1.00
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Sidewall boundary layer upstream of cascade
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Isentropic Mach number distribution at the sidewall without coolant ejection (Ma2is=1.00)
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Oil flow picture of sidewall together with velocity vectors measured by L2F at a wall distance of 0.5 mm, without coolant ejection
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L2F measurements at x/lax=0.10 and at two wall distances (z=0.5 and 20 mm), without coolant ejection; contour Mach number from a profile pressure distribution measurement at z=20 mm
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L2F measurements at x/lax=0.35 and at two wall distances (z=0.5 and 20 mm), without coolant ejection
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L2F measurements at x/lax=0.10 with coolant ejection from the holes only
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L2F measurements at x/lax=0.35 with coolant ejection from the holes only
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L2F measurements at x/lax=0.10 and at the wall distance z=0.5 mm(z/h=0.004); without coolant ejection and with coolant ejection from the slot only
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Coolant concentration from slot ejection at x/lax=0.10
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L2F measurements at x/lax=0.35 and at the wall distance z=0.5 mm(z/h=0.004); without coolant ejection and with coolant ejection from the slot only
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Coolant concentration from slot ejection at x/lax=0.35
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Oil flow picture of the endwall together with velocity vectors measured by L2F at a wall distance of 0.5 mm, with coolant ejection from slot and holes
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Coolant concentration in plane x/lax=0.10 with coolant ejection from slot and holes
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Overview of flow values in plane x/lax=0.35 with coolant ejection from slot and holes
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Overview of flow values in downstream plane x/lax=1.10 with coolant ejection from slot and holes
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Pitch-averaged flow values at x/lax=1.10,Ma2is=1.0
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Area-averaged energy loss values with the area extending from z=2 mm to 30 mm (z/h=0.016 to 0.24); coolant ejection from slot and holes

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